U.S. patent number 3,860,930 [Application Number 05/390,998] was granted by the patent office on 1975-01-14 for radar antenna scan apparatus.
This patent grant is currently assigned to Texas Instruments Incorporated. Invention is credited to Robert K. Peterson.
United States Patent |
3,860,930 |
Peterson |
January 14, 1975 |
RADAR ANTENNA SCAN APPARATUS
Abstract
A radar antenna scan drive employs a planetary type drive. An RF
antenna is fixed to rotate with a planet gear while the planet
rotates around a sun gear. The swept volume of the RF antenna, as
it scans, is shaped to be noncircular by the ratios selected for
the planetary drive. The swept volume shape is utilized to package
a larger RF aperture antenna in a fixed available space that is not
circular.
Inventors: |
Peterson; Robert K. (Garland,
TX) |
Assignee: |
Texas Instruments Incorporated
(Dallas, TX)
|
Family
ID: |
23544803 |
Appl.
No.: |
05/390,998 |
Filed: |
August 23, 1973 |
Current U.S.
Class: |
343/705;
343/766 |
Current CPC
Class: |
H01Q
1/281 (20130101); H01Q 3/04 (20130101) |
Current International
Class: |
H01Q
3/04 (20060101); H01Q 1/28 (20060101); H01Q
1/27 (20060101); H01Q 3/02 (20060101); H01q
001/28 () |
Field of
Search: |
;343/759,763-766,705 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Lieberman; Eli
Attorney, Agent or Firm: Levine; Harold Grossman; Rene E.
Bandy; Alva H.
Claims
What is claimed is:
1. A radar scan apparatus for translating a rotating antenna within
a confined conical shaped space in an aircraft for increasing the
size of the antenna aperture for an antenna system comprising:
a. a drive shaft;
b. means coupled to the drive shaft for rotating the drive
shaft;
c. a support means including a first support member attached to the
drive shaft for rotation therewith, and a second support member
rotatably mounted in said first support member, said second support
member eccentrically disposed to the drive shaft;
d. an antenna attached to the second support member for rotation
therewith; and
e. a drive means responsive to the rotation of the drive shaft for
rotating the second support member and its antenna one half
rotation in a direction opposite to that of the first support means
for every rotation of the first support means whereby when said
first support member is in the rearmost position the antenna
extends with its maximum dimension perpendicular to the center line
of the aircraft and moves the rotating antenna within a
substantially triangular envelope to conform to the walls of the
confined conical shaped space.
2. A radar scan apparatus according to claim 1 wherein said drive
means includes a planetary gear mounted on a shaft of the second
support member and at least a section of a ring gear attached to
the aircraft within the confined conical space, said planetary gear
meshing with the ring gear and driven by the first support member
attached to the drive shaft.
3. A radar scan apparatus according to claim 1 wherein said drive
means includes a first pulley attached to the second support
member, a second pulley attached to the drive shaft, and a belt
interconnecting the first and second pulleys, said first and second
pulleys having a size ratio of 1:1.5.
Description
The present invention relates generally to improvements in aircraft
radar antenna scan apparatus. In another aspect, this invention
relates to a new and improved antenna scan apparatus which
increases the possible antenna aperture size for an antenna system
which is scanned or rotated within the limited space available in
the nose of an aircraft.
Problems in radar systems in aircraft involve space and weight
requirements. Most military aircraft do not permit heavy and bulky
radar apparatus. Space and weight limitations in small lightweight
aircraft can be even more critical.
Performance requirements of a radar are based on its intended
mission. Often a larger antenna RF aperture is required for a
mission than is possible in an existing aircraft radome with
conventional antenna scan apparatus.
It is often necessary to place radar antennae in the front or nose
section of the aircraft. Front sections, due to aerodynamic
considerations, must be generally cone-shaped or tapered. Space
requirements of the moving radar antenna and an associated scan
drive present serious design problems.
Therefore, there exists a need for a compact and lightweight RF
antenna and associated scan drive which may be accommodated in the
confines of the nose of the aircraft.
By the present invention, there is provided a system with an
antenna having an improved scanning apparatus which optimizes the
use of space available for both a 360.degree. scan and a sector
scan application.
By the present invention, a directional antenna is rotated about an
axis perpendicular to the scan plane. Means are provided to cause
the axis of rotation of the antenna to translate with respect to
the aircraft so that an antenna of maximum size may rotate within
the nose of an aircraft, allowing the use of an antenna with a
large aperture area.
More particularly, a shaped swept volume is achieved by mounting
the antenna in the nose of an aircraft by means of an epicyclic
drive. The drive in one form, a gear train, includes an internal
tooth ring gear fixed to the aircraft in a plane with the axis
thereof parallel to the axis of rotation of the antenna. A
planetary gear is positioned to rotate inside and mesh with the
ring gear. A drive mechanism rotates the planetary gear axis while
the gear is meshed with the ring gear. The antenna is fixed to
rotate with the planetary gear.
In accordance with a further aspect of the present invention, the
pitch diameter of the ring gear is selected to be exactly one and
one-half times the pitch diameter of the planetary gear for a
360.degree. scan. The antenna is so positioned on the planetary
gear such that when the planetary gear is in the rearmost position
on the ring gear, the antenna extends with its maximum dimension
perpendicular to the center line of the aircraft. For sector scan
only applications, the ring gear to planet gear ratio may be varied
for specific shaping results.
In accordance with the invention, an aircraft radar scan apparatus
rotates the directional antenna about an axis perpendicular to a
scan plane. The physical distance between the ring gear axis and
the planetary gear axis influences the swept volume shape generated
during scan. Therefore, the geometric location of rotational axes
must be specifically matched with each particular application.
For a more complete understanding of the present invention and for
further objects and advantages thereof, reference may now be had to
the following detailed specification taken in conjunction with the
accompanying drawings in which:
FIG. 1 is a side elevation view of a typical aircraft showing the
aerodynamic profile of the nose containing an aircraft radar;
FIG. 2 is a plan view of a sector scan antenna with one embodiment
of the improved scan apparatus;
FIG. 3 is a plan view of two sector scan antennae rotated through
identical scan angles illustrating the increased antenna aperture
attained by the present invention;
FIG. 4 is a front elevation of a 360.degree. scan antenna involving
a second embodiment of the present invention;
FIG. 5 is a section view taken on line 5--5 of FIG. 4;
FIG. 6 is a plan view of the apparatus of FIG. 4;
FIG. 7 illustrates the path of movement of the antenna as it is
rotated in accordance with the present invention;
FIG. 8 is a view similar to FIG. 7 illustrating another portion of
the scan cycle;
FIG. 9 is a view similar to FIG. 7 illustrating the path of
movement of an antenna through a complete cycle by both a
conventional apparatus and by the present invention;
FIG. 10 illustrates a belt driven epicyclic system; and
FIG. 11 illustrates shaping variations.
Referring now to the drawings wherein like reference characters
designate like or corresponding parts throughout the several views,
there is illustrated in FIG. 1 a portion of an aircraft, which for
purposes of description is identified by reference numeral 10.
Illustrated aircraft 10 is of the high performance type having a
sleek profile.
Aircraft 10 is illustrative of aircraft which, due to high
performance, have a generally tapered or conical nose 12. Nose 12
normally houses a forward looking sector scan radar apparatus. The
size and shape of the space within nose 12 are dictated by the
aerodynamic requirements of the aircraft. The size and space are
fixed and dictate the limits that may be accepted by a radar
unit.
In FIG. 2, one embodiment of an antenna structure 14 and scan
apparatus of the present invention is illustrated in position
within nose 12. Antenna 14 is of a conventional parabolic design
with a reflector mounted therein for receiving and transmitting
radar signals in a conventional manner. It is to be understood that
other antenna shapes and structures could be utilized with the
apparatus of the present invention and that the parabolic shape is
shown for illustrative purposes only. The antenna aperture L is
maximized by use of the improved antenna scan apparatus 16 of the
present invention. The embodiment illustrated in FIG. 2 is utilized
in scanning the antenna about an angle less then 360.degree.. For
purposes of description, the antenna is mounted for rotation
through a 60.degree. scan angle with the antenna rotating
30.degree. either side of the center line 18 of the aircraft.
Scan apparatus 16 has an epicyclic gear train which is attached to
antenna 14 to rotate the same as desired. In the embodiment
illustrated, a portion of an internal ring gear 20 is fixed to the
frame of aircraft 10 in a position located immediately behind the
antenna 14 and in a plane parallel to the scan plane. Ring gear 20
has internal teeth thereon which mesh with a planetary gear 22.
Planetary gear 22 has a central shaft 24 which is attached to an
arm 26. Arm 26 is attached to antenna 14 so that antenna 14 rotates
with and about the center of planetary gear 22. A second arm 28 has
one end rotatably attached to shaft 24 and the other end attached
to a drive shaft 30. Shaft 30 is positioned to rotate about an axis
colinear with the center of ring gear 20. Arm 28 maintains
planetary gear 22 meshed with ring gear 20 to translate shaft 24
and antenna 14 around gear 20.
A suitable driving motor 31 is operationally connected to drive
shaft 30 to cause the shaft 30 to reciprocate through a 90.degree.
angle symmetrical to line 18. The pitch diameter of the ring gear
is one and one-half times the pitch diameter of the planetary gear
such that 60.degree. rotation of the arm will result in 90.degree.
of rotation of the planet axis. The result is a .+-.30.degree. scan
of the antenna RF beam.
By utilizing the improved antenna scan structure, a significant
percentage increase in possible antenna aperture area can be
achieved relative to conventional antenna scan apparatus. This
improvement is illustrated in FIG. 3 wherein a conventional antenna
32 pivots about point 34 positioned behind the antenna 32. The
maximum antenna aperture M is illustrated for an antenna which is
rotated 30.degree. either side of the center line 18 of the
aircraft as required.
In contrast, antenna 14 is in phantom lines in the plus and minus
30.degree. positions characterizing use of the present invention.
The maximum antenna aperture is of width L. Aperture width L is 18
percent greater in this example than aperture width M. Therefore, a
substantial increase in performance of the antenna 14 over the
antenna 32 is achieved.
As can be seen in FIG. 3, when it is desired to rotate the antenna
in a clockwise direction from the position illustrated in solid
lines, the scan apparatus rotates the center of rotation of shaft
24 counterclockwise along gear 20 to a point 24a further away from
the walls of nose 12. Likewise, when it is desired to rotate
antenna 14 counterclockwise from the position shown in solid lines,
shaft 24 moves clockwise along gear 20 to the position 24b. Thus,
pivot 24 moves away from the wall of nose 12, allowing for an
increase in the antenna size and aperture.
By utilizing the present invention, antenna 24 scans a set angle
while providing a larger aperture, an increase in efficiency and
performance of an antenna in a given space is achieved.
Turning now to FIGS. 4-8, a second embodiment of the invention is
illustrated. In this embodiment, an antenna 40 is illustrated. An
epicyclic gear train is utilized to rotate antenna 40 through
360.degree.. The drive apparatus comprises a fixed internal tooth
ring gear 44 attached to the frame of aircraft 10. A planetary gear
46 is mounted within ring gear 44 to mesh with and rotate about the
interior of gear 44. The diameter of the ring gear 44 is selected
to be exactly one and one-half times that of the pitch diameter of
the planetary gear. A shaft 48 is fixed to planetary gear 46 and
antenna 40. An arm 50 is rotatably attached to shaft 48. A drive
shaft 52 is positioned to rotate about the center line of gear 44
and is attached to the arm 50. A suitable driving means 54, such as
a motor, is attached to the drive shaft 52 to rotate drive shaft 52
about the center line of gear 44 and thus move the planetary gear
46 around the interior of gear 44.
As best seen in FIG. 6, the alignment is such that the arm 50
extends along the center line of the aircraft from the center of
the ring gear in a direction toward the rear of the aircraft when
the antenna is aligned with the center line and is facing in a
forward direction. In this position, the rear surface of antenna 40
is closely adjacent to a rear bulkhead 56. As the arm 50 is rotated
in a clockwise direction, as seen in FIG. 6, the antenna will make
one-half rotation counterclockwise for every rotation of arm 50 in
gear 44. During this movement, the antenna will move and its
movement will be confined within the envelope 58 which is shown in
dotted lines in FIG. 7.
As planetary gear 46 moves around ring gear 44, antenna 40 will
successively move between and assume the positions 40', 40a and 40b
in FIG. 7. In position 40a, the antenna is directed to the front
and port side of the aircraft. In position 40b, the antenna is
directed to the rear and port side.
Continued movement of planetary gear 46 around ring gear 44 will
cause the antenna to successively move to and between positions
40c, 40d, 40e (FIG. 8) and return to position 40' (FIG. 7). In
position 40c, the antenna is pointing to the rear and in 40d to the
rear and starboard. In position 40e, it is pointing forward and
starboard. Upon returning to position 40', the antenna is again
pointing forward.
By utilizing the present invention, antenna 40 will rotate within
envelope 58 and substantially conform to the walls of a
conical-shaped nose portion 12 permitting an increase in the
effective aperture of antenna 40.
In FIG. 9, this increase in aperture is illustrated with the circle
70 representing the envelope of movement of an antenna rotated by
conventional scan apparatus. Triangular envelope 58 illustrates the
movement of the antenna in accordance with the present invention.
The width of the aperture of the antenna which assumes the envelope
of motion 70 is represented by dimension A which is substantially
smaller than dimension B which represents the width of the aperture
of an antenna rotated by the apparatus of the present
invention.
By constructing antenna and scan drive apparatus in the manner
described herein, the space envelope required for a 360.degree.
scan of the antenna has a general equilateral triangular shape with
rounded corners. When viewed in a plane parallel to the scanning
plane, the triangular shape has one leg extending transverse to the
center line of the aircraft and the other two legs extending
generally along and parallel to the tapered walls of the nose
portion of the aircraft.
It is therefore to be understood, of course, that the apparatus of
the present invention provides an antenna scan apparatus which is a
simple, lightweight mechanism, yet substantially increases the
aperture of the antenna which is limited to operate within a given
space.
FIG. 10 illustrates a belt driven epicyclic system in which the
antenna dish 40 is mounted to rotate on the shaft 100 of a
planetary gear 101. Gear 101 is mounted on an arm 102 which is
driven by a motor 103 by way of the shaft 104. The shaft 104 is
journaled in bearings 105 and 106. Bearing 105 is supported in a
frame member 107. A bracket 108 is mounted on frame 107 and support
bearing 106. A fixed sun pulley 109 is rotatably mounted on the top
of the bracket 108. A belt 110 then couples the pulley 109 to the
pulley 101.
With the ratio of the sizes of pulleys 101 to 109 being 1:1.5, then
the swept volume of the dish 40 will be the same as that
illustrated in FIGS. 7 and 8. The drive of FIG. 10 eliminates the
need for an internally toothed sun gear as of the type illustrated
in FIG. 6 but provides the same motion. Preferably belt 110 is of
the well known timing belt variety. The same variables are possible
using the system of FIG. 10 as in altogether embodiments.
FIG. 11 illustrates variations in shape of the swept volume that
can be achieved by varying the offset between the sun element and
the planetary element. For example, variations in the distance
between the axis of shaft 100 and shaft 104 for a given size of
dish 40 will alter the nature of the swept volume. For example,
with the dish having a width of 56 inches and the arm of 9 inch
length, the swept volume had the pattern 120. With a 7 inch arm,
the volume had a pattern 121. With a 6 inch arm, the volume had a
pattern 122 and with a 5 inch arm, the volume had a pattern 123.
The shorter the arm the more nearly the swept volume becomes
rounded or circular. The longer the arm relative to a given dish
width, the more the size of the swept volume becomes dished.
The shape of the swept volume can further be altered by offsetting
the tips or maximum chord of the dish 40 from axis 100, FIG. 10.
That is, the dish may be mounted for rotation on shaft 100 where
the axis does not pass through the widest point on the dish. For
example, the dish 40 might be moved forward so that the dotted line
130 coincides with the axis of shaft 100. Alternatively, a mounting
bracket could be used so that the axis 100 corresponded with the
location of dashed line 131.
It will be apparent from a discussion of FIG. 10 that the arm
length as used with respect to the distance between the axes of
shafts 100 and 104 has its counterpart in the systems using the sun
gear and ring gear combination. The arm is the distance between the
axis of the sun and the planet gears. The present invention,
therefore, involves the method of shaping the swept volume of radar
scan unit by supporting and moving the scan unit on and with a
planet member of an epicyclic drive.
Having described the invention in connection with certain specific
embodiments thereof, it is to be understood that further
modifications may now suggest themselves to those skilled in the
antenna art and it is intended to cover such modifications as fall
within the scope of the appended claims.
* * * * *